Missile launching system



Jan. 26, 1965 s. LANDsTRoM ETAL MISSILE LAUNCHING SYSTEM Filed Oct. 22. 1958 5 Sheets-Sheet l Jan. 26, 1965 Filed Oct. 22, 1958 s. LANDsTRoM ETAL MISSILE LAUNCHING SYSTEM 5 Sheets-Sheet 2 INVENTORS SVEN LANDSTROM ROBERT E. GARLBERG MKM ATTORNEYS s. LANDsTRoM ETAL 3,166,975

MISSILE LAUNCHING SYSTEM Jan. 26, 1965 5 Sheets-Sheet 3 Filed OC. 22, 1958 INVENTORS ROM ROBERT CARLBERG BY QL/Ww- @www Jan. 26, 1965 s. LANDsTRoM ETAL. 3,166,975

MssILE LAUNCHING SYSTEM 5 Sheets-Sheet 4 Filed Oct. 22, 1958 INVENTORS SVEN LANDSTROM ROBERT E. CARLBERG W/QM .ATTORNES www Om wJ-ww-E M O@- ,A

5 Sheets-Sheet 5 S. LANDSTROM ETALl MISSILE LAUNCHING SYSTEM Jan. 26, 1965 Filed oct. 22, 195s United States Patent() MISSILE LAUNCHENG SYSTEM Sven Landstrorn, Stockholm, Sweden, and Robert E. Carlherg, Fails Church, Var, assignors to the United States of America as represented hy the Secretary of the vNavy Filed Oct. 22, 1953, Ser. No. 769,844 y 3 Claims. (Cl. 89'-l.7)

(Granted under Title 3S, US. Code (i952), ser. 266)' The invention described herein may be manufactured and used by or for theV Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

The present invention relates to missile launching systems and more particularly to a system which includes a magazine and associated hoist and ramming mechanisms by means of which missiles may be loaded onto the launchers and iired. The present system is particularly adapted for shipboard use although it may be satisfactorily employed as a stationary land based weapon.

Previous types of missile launching systems have not been entirely satisfactory under the severe service conditions imposed by shipboard mounting. One of the significant disadvantages of the prior art launching systems resides in the fact that none of these systems provides a closely integrated combination of components capable of the required' coordinated sequential operations of handling missiles from their arrival on the ships deck through the decanning of the various components of each missile, the assembly of the components to form a single missile, transferring the plurality of assembled missiles to a storage space, and then, during the tiring cycle, transferring the missiles from their storage space to a launching device, all of the recited operations being performed while the missiles are maintained in a horizontally disposed position. Although numerous launching'systems are known, many of these systemsv involve movements or operations which cause the delicate missiles to be jostled about thereby causing the misalignment of the delicate electronic and other components of the missile and precipitating many equipment failures which effectively prevent a successful and sustained launching evolution.

ln addition, none of the launching systems of the prior art performs Athe operations aforo-mentioned in close confinement and without, at any time, exposing the storage area to water, blast etlect from either adjacent launchers or enemy action. Furthermore, none of the launching systems heretofore known, is as readily installed on different types of ships having various depths and width characteristics. Y

Consequently, with the foregoing shortcomings or disadvantages of the prior art launching systems in mind,V it is an object of thepresent invention to provide a launching system capable of handling missiles in a horizontally disposed tposition from their arrival on the` ships` deck through the decanning operations of the various components, the assembly of these components into missiles and the transfer or" the substantially completely assembled missiles to a'rmagazine or missile StorageV area.

Another object of the invention residesiri the provision ofv a missile Vlaunchingrsystem capable of transferring missiles from a below deck storage area, during the iring cycle, to a superposed wing and iin attachment station,

` ramming the missiles horizontally from the attachmentr grated elements and mechanisms Within a launching system for missilesand adapted for operation in close continement without at any time exposing the storage area to ice water, blast effect from the launcher of the system, from adjacent launchers, or from enemy action.

A further object of the instant invention is the provision of a composite missile launching installation for firing missiles singly or in salvo and rwhich provides for a plurality of individual systems normally isolated from one another but which may be interconnected if desired for the transfer of missiles therebetween.

Still another object of the present invention resides in` the combination of various integrated mechanisms of amissile launching system which has a high degree of ilexibility thereby facilitating installation of the system in different types of ships having various beam and depth characteristics.

A further object resides in the provision of a missile launching system in which any one oi a number of different types of missilesmay be selected from the magazine for launching.

Other objects and many voli the attendant advantagesv of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

PEG. l is a side elevation oi one embodiment of the invention with parts in section, showing the arrangement of the magazines and their associated launching devices and taken along a line substantially corresponding to line l-l in HG. 2;

PEG. 2 is a rear elevation view of the system of the embodiment illustrated in FIG. l, with parts in section, and taken along a line substantially corresponding to the line 2--2 in FlG. l;

FlG. 3 is a perspective view of the missile storage. shelves and the missile hoist within the magazine or storage area showing the relationship of the structure of the hoist and the shelves in the magazine area;

FIG. 4 is a fragmental sectional view of the hoist chain guide and hoist chain showing the manner in which the hoist chain is affixed tothe hoist proper;

FG. 5 is a sectional view taken along a line substantially corresponding to line 5-5 of FIG. 4 and showing the horizontal cross ksection of the hoist chain and the manner in which the hoist chain is affixed to the hoist;

HG. 6 is a fragmental exploded perspective view showing the contiguration of the buckle located von one end of. the transfer bars oi the missile storage shelves and the mating portion or catch of the transfer chain carried interiorly of the hoist;

FlG. 7 is a plan view of the rammer chain and rammer head and their relative arrangement in the rammer rail;

FIG. 8 is a front vertical elevation View, with parts in section, showing the manner in which the rammer rail. is configured to hold the rammer mechanisms;

FIG. 9 is a side elevation view, with parts in section,

showing the rammer rail and the position to which the.

be observed that the launcher employed in the system of` y the present invention and which is generally referred to by reference numeral 10 has twin launching arms 12, each of which isl provided with an overhead launching rail 14 for receiving a missile 30 during the loading operation. Missiles 30 may be launched from rails 14 when launcher l 10 is elevated andtrainedto a predetermined launching position. The structural details of the launcher, except as specifically noted hereinafter, form no part of the present invention, and therefore, etailed reference thereto is believed unnecessary in this application. However, for additional details of a suitable launcher, reference is made to the copending application of Ferdinand J. Schiavi, Serial No. 252,970, filed October 24, 1951, which matured into U.S. Patent No. 2,826,960 on March 18, 1958. This patent `discloses a launcher similar in many respects to the launcher disclosed herein. Y The launcher generally consists of a pedestal 16, about the vertical axis of which the launcher is trainable, and a pair of launcher arms 12 which-may be rotated around suitable trunnions 15 by means of elevation pinion 17 meshing with the teeth of elevation arc 18 for providing the angle of elevation proper for launching. Mounted on the forward portion of each launcher arm 12 is shown a suitable back-scratcher 20, the function of which will be described more fully hereinafter. Immediately behind each launcher and in horizontal alignment therewith is located an area 22 utilized primarily for attaching the fin and tail elements to the missile. y the iin and tail attachment area 22 is the ramming mechanism 24 which consists essentially of an extendable rammer chain 25, a drive sprocket 26, a suitable motor V27, gear reduction box 29 and an idler sprocket 28 which Suspended from the overhead or ceiling 23 of serves to guide the exible chain Within its chain guide.

The rammer chain (FIG. 7), the hoist transfer chain 120 (FIG. 6), and the hoist chain 95 (FIG. 2) are all of the same general configuration and constitute what is generally termed an extendable or unidirectional chain. The chain 25 (see FIGS. 7 and 10) is made up of links 32 connected pivotally together and carried by rollers 33 which ride in suitable tracks provided within the chainV guide 34. The chain links are shaped so as to allow the chain to ex or bend in a direction toward the rollers while preventing any exure in other directions. By use of a chain of this type a force may be exerted to ram, that is, push or pull while the chain may be folded upon itself to conserve space. The details of .the particular chains disclosed herein are not intended to form any part of this invention and any suitable chain may be utilized as, for example, the chain disclosed in the copending application of Robert E. Carlberg et al., Serial No. 466,462, eld November 2, 1954, which matured into U.S. Patent 3,001,454 on September 26, 19.61.

In like manner, the details of the drive motors and sprockets used to power the extendable rammer, transfer and hoist chains, hereinafter more fully explained, are not important to an understanding of the instant invention. Any conventional drive motor, and gear train may be successfully employed to practice the invention and any of the well-known expedients within the province of the skilled worker are intended to Vbe within thescope of the invention disclosed. By way of example, a suitable power drivermay comprise an electric motor mechanically connected to a hydraulic pump which is, in turn, hydraulically connected to a hydraulic motor on each drive sprocket.

Separating the n and tail attachment station or area 22 from the launcher'lil is a pair of blast doors 54 which are hinged to swing horizontally in their opening action in order to expose the tin and tail attachment area 22 to the launcher 10. A vSpanner rail 40 serves to bridge the gap between the rammer rail 31, located in the iin and tail attachment area yor station, and the launcher rail 14, which is depressed to a horizontal position as shown in FIG. 1 for loading. The Spanner rail 40 may be integral with bell crank 43, which is connected to the tin and Y tail attachment housing by pivot 47 and around which it is rotated by the actuator cylinderV 50. The actuator cylinder is Vpreferably hydraulically or pneumatically operated, in which case it is Vconnected to a source oftluid under pressure, not shown. Y The Spanner rail 40 'isof ner rail.

Vknown type.

siles 30 to be moved along the rails by the rammer head 21, as will be explained more completely hereinafter. The ends 41 of the Spanner rail are beveled to abut against the mating bevel of the extremitiesrof launcher rail 14 and rammer rail 31. When the ramming operation is to be commenced, blast doors 54 are opened and the iluid cylinder S0 is actuated to pivot bell crank 43 around point 47 to raise Spanner rail 40 to the horizontal. The beveled ends of the rammer rail abut the mating ends of the normally spaced launcher and rammer rails Vto form a continuous overhead monorail for sliding the missiles from the n and tail attachment station 22 to the tiring position on the launcher rail 14. To assure that the spanner rail remains xed in horizontal position, suitable latches or interlocks 51 may be provided to hold the rails together. These latches may be of any well- For example, they may comprise tapered pins reciprocallycarried in latch bores in remote ends of the Spanner rail bell crank 43. Registering bores may be provided in the biased abutting 'ends 4ofthe launcher arm 12 and rammer rail support 52. Air or any suitable tiuid may conveniently be tapped off'from the same sour used to raise the Spanner rail and be introduced into the bores in the bell crank behind the tapered pins. The pressure will move and hold the pins in contact with the Y interior of the mating bores provided in the launcher arm and rammer rail support and which will register properly when the Spanner rail is horizontal. When it is desired to restore the Spanner rail 40 to its original housed position, as for example, when a missile is to be launched, the air pressure holding the pins may be releasedand the pins may be retracted to within the span- A conventional spring biasing device may conveniently be used to assure rapidY return of the pins to their unlatched position. It should be understood, of course, that the latches described 'are merely intended to be illustrative and other suitable expedients, such as solenoid operated latches or the like could-be employed. In FIG. 1 there Vare shown two systems arranged in tandem, that is, with the launcher 10 lof the rearward system vertically disposed over the 1in and tail'assembly station 22 of the forward system. When such an arrangement is utilized, it is desirable to position a blast detlector 55 on the forward edge of the housing of the fin and tail attachment station of the forward system to shield the superposed launcher of the after system, as illustrated. When arranged in this manner, the strike down areas 58 ordinarily employed with a single dualV rail overhead launching system may adequately serve two dual rail overhead-launching systems as illustrated inV FIG. l, or in some installations severalrsystems. It will be understoodY that each system, if not employed in tandem relationship'with other like systems as illustrated, or in close adjacency thereto, will be provided with a strike-down area or areas individual thereto. This description is conned to Va shipboard installation, although, as pointed out hereinbefore, thel systemy may be employed with advantageous results in any permanent type of installation.

The dualV strike-down Aareas 58, like the dual fin and tail attachment Vareas 22, are disposed in a side-by-sideA relation with each other and may be enclosed in any-suitable manner by exterior walls 60. These areas may be separated by interior partition wallsv 62. Within the strikedown areas, missile components as received from a depot or an ammunition ship maybe decanned and preassembled to form substantially complete missiles 64. The `wing and n portions are preferably assembled just prior to the ramming operation,'as will become more fully apparent as the description proceeds. The strike-down areas are also conveniently Vequipped to serve as a repair shop for the correction of minor mechanicalrand electrical defects discovered in the missiles. Each of the `dual strikedown areas 58 is provided with a trap door assembly 66 blies may advantageously also be provided with hydraulic actuating cylinders 70 and 72 which serve to open the door to provide access between the areas and the magazine or missile storage area 76 of the launching system. The undersurface of each door is preferably provided with guide rail extensions '78 which serve, as will be explained more fully hereinafter, as extensions of the vertical guide rails 79 located within the magazines and which cooperate with the guideways Sil in the hoist 85 to assure that the hoist moves in a vertical direction. Fixed rails 82 may be positioned in the strike-down area 5S to bridge the space between the rail extensions 7 8 on doors 66 and 68.

Like the actuator t) for the Spanner rail, the trap door actuators 72, 70 are preferably connected to a suitable source of fluid under pressure, not shown. It should be understood that although disclosed as being hydraulically actuated, these elements may be actuated by air pressure or any other well-known actuating means.

As illustratd in FIG. 1, when the systems are arranged in tandem relationship, the strike-down areas 5S may serve both magazine systems, and when such is the case, a suitable door or hatch 35 is located in the interior wall or bulkhead 36 to permit introduction of partially assembled missiles from the strike-down areas 58 of the after system into the n and tail attachment areas 22 of the forward missile handling system. Except for the interconnecting hatch or door 35, the systems are isolated from each other by walls 36. As illustrated in FIG. 2 the separate forward and after launching systems may be further compartmented into system halves, each half being adapted for supplying missiles to one or the other of the dual rails 14 of the launcher lt). A suitable door or hatch 44 is also located in the outer wall or bulkhead 69 of the strike-down areas of the after system to facilitate introduction of the missiles from the ships deck into the composite missile launching system. When the missiles are partially assembled, after the decanning operation in the strike-down area 5S, the missiles may be hoisted or lifted onto the hoists 85 to be lowered through the open doors 68, 66 into the storage areas 76. Any suitable auxiliary handling means such as a winch (not shown) may be located in the strike-down area to facilitate this procedure.

Below the lin and tail attachment stations 22 of the forward system and the strike-down areas 58 of the after system are located the magazine or storage areas 76 of the composite system or installation. A series of vertically arranged shelves 8S of cantilevered construction are suitably welded or otherwise aiixed to the bulkheads of the magazine and serve to hold the missiles during storage.

Referring more particularly now to FIG. 2, it will be observed that a longitudinal bulkhead or central support 87 serves to support one end of each missile storage shelf. A space 90 is preferably provided between the longitudinal bulkheads or central support 87 of adjacent storage areas 76 to serve as a storage space for extendible hoist chain V95 and chain guide 94 of the system, which may be of the same type as the previously described rammer chain. Each shelf 8S is illustrated as holding three mis- Siles although it should be understood that the shelves could be longer or shorter, depending upon the beam characteristics of the vessel with which the system is ernployed in which case fewer or more missiles will be stowed thereon. Above each tier of missiles, there is located a rammer yoke 19t? which serves, as will be more fully explained hereinafter, to move the missiles longitudinally in the storage area. Adjacent the distal ends of the shelves there is provided a hoist 85 which, constrained by its vertical guide rails 79, and actuated by the extendible hoist chain 95, moves vertically through the magazine area to raise and lower the missiles. The vertical guide rails '79 are held by brackets S4 which are fastened in any well-known manner to the exterior bulkheads of the storage areaV 76. Actuating means for the hoist chain are located, in vthe illustrated embodiment, at the bottom of the storage area and may consist of a motor 91, a gear reduction box 92, a pair of bevel gears 93, driving a drive sprocket 96 which engages the hoist chain in a conventional manner to raise and lower the hoist. Adjacent longitudinal bulkheadv 87 is positioned an idler sprocket 97 which serves to urge the flexible chain up into the housing provided in the space separating the longitudinal bulkheads of adjacent storage areas or magazines. The chain for the hoist is guided in its path by meansy of a suitable chain guide 94.

Above each storage area76 is located a fin and tail attachment station 22 in which is positioned a pair of tween decks 37 which serve to provide support for personnel working in that space. Within this area 22 there may be provided a plurality of bins 38 which, as illustrated, serve to hold the tin and tail elements 39 which are preferably athxed to the missiles just prior to the ramming operation for ease of stowability of the missiles.

As a missile is elevated from its storage shelf, the hoist 85 riding along its vertical guide rails 79, elevates the missile to the position shown in the left-hand portion of FIG. 2. In that position the missile handling lugs 101, located on the upper side of the missile, are in a position to be engaged by the rammer mechanism, as will be explained more fully hereinafter. The hoist holds the missile in the position indicated, by engaging the bottom handling lugs of the missile, while personnel atlix to the missile surfaces the required number of iin and tail surfaces 39. As illustrated, the trap door 63 is actuated by means of an actuator cylinder 72 to open the trap door and thus provide communication between the fin and tail attachment station 22 and the storage area 76. On the right-hand side of FIG. 2 there is illustrated a completely assembled missile 3-9 with its n and tail attachment surfaces 39 in place. It will be seen that the missile is supported by means of its upper handling lugs 101 by the ramming mechanism and the hoist may be retracted to a position Within the storage area '76. The trap door 63 may be lowered to provide a solid deck separating the n and tail attachment station from the storage area. The vertical guide rails 79 which restrict the hoist to vertical movement, terminate adjacent the upper tier of missiles. However, the guide rail extensions 78 located on the undersurface of each door serve, when the door is open, to form an extension of the vertical guide rails Vso that the hoist may be controlla ly elevated high enough to cause the ramming mechanism to engage the upper handling lugs of the missiles. The xed guide rails 82 serve the same function between doors 66 and 68. Locatedl above the tin and tail attachment station of the forward system there is illustrated the launching mechanism 1li which is an element of the after system shown in FIG. l. Suspended from the overhead or ceiling 23 of'the hn and tail attachment stations 22 are the ramming mechanisms for each arm of the dual launchers.

Referring now more particularlyto FIG. 3, there is shown above eachV tier of missiles in the stowage areas a rammer yoke 160 which is suitably connected by means of brackety 194 to thestructure of the ship. A hydraulic actuator cylinder 196 serves to reciprocate the rammer yoke longitudinally of the storage area. Fastened to the bracket 164 are longitudinal guide bars 105 which coopern ate with the yoke keyways 19S to assure-only longitudinal movement of the rammer yoke. A groove runs transversely along the undersurface of the rammer yoke. This groove is so proportioned as to enable the rammer yoketo engage the upper missile handlinglug 191 located on the after end of the booster section of each missile on ashelf.

The shelves 88 -are made up of fixed portions 114 andV transversely movable portions or transfer bars 116. The transfer bars 116 are mounted so as when properly vactuated, as will be further explained hereinafter, they will;

move transversely of the magazine or storage area. The surfaceof the hoist is provided with transverse channels 118 adapted to receive the transfer bars 116. Hoist transfer chains 120 shown in FIG. 6 but omitted from FIG. 3 for clarity, are .located within the hoist and are guided by means of their chain channels 122 for movement in predetermined paths within the hoist. The hoist transfer chains are driven transversely of the hoist by drive sprockets 121 keyed or otherwise suitably fastened to a shaft 123. The shaft rotates around its end bearings 124 when sprockets 121 are driven through chain drive 125 and reduction gear train 126 by means of motor 128. The working end of the hoist transfer chain 120 is provided with a T-catch 119 which, as can be observed from FIG. 6, is configured so as to engage transfer bar buckle 117 to pull the transfer bars 116 into the transfer bar channel 113. The T-catch 119 may normally slide vertically through transfer bar buckle 117 without frictional contact, land in normal raising or lowering of the hoist, the buckle allows free passage of the T-catch therethrough without any binding or movement of the transfer bars.

However, when the Vhoist is aligned Vwith the shelf, as illustrated in FIG. 3, the T-catch is confined or surrounded by the .buckle of the transfer bar. Upon actuation of motor 128, the drive sprockets 121 cause the hoist transfer chains tobe retracted within theirV guides and the transfer bars 116 are moved transversely into the transfer bar channels 118 in the hoist proper. 1 y

A pair vof auxiliary hydraulic jacks 1.3i), 131 are mounted in opposed relationship within the hoist 85. They may be connected to a source of fluid pressure (not shown)Y and serve to move the missiles longitudinally on the hoist. Each jack is provided with a boss 132 which abuts against the after missile handling lug 191 to move the missile longitudinally in the slots 102 in the hoist surface. i

The shelves of the magazine system as well as the face portion of thehoist are provided with grooves or notches so configured as to correspond with the shape of the missile handling lugs 101 located on the forward and after ends of the missile lbooster section. Both the transfer bars 116 and the fixed yportions 114 'of the shelves are provided with grooves 134, 135 respectively, and when the transfer bars are aligned, asshown in FIG. 3, theV grooves register or coincide to form one continuous groove extending from thetransfer bars into the fixed portion of the shelves. The grooves or notches 102 formed inthe upper surface of the hoist are identical with those in the shelves except .that extra cutaway portions 103 are provided to facilitate removal of the missile from the hoist, as will be more fully explained hereinafter. When in a stowed position on the shelves, the lower missile handling lugs of the stowed missiles are positioned within the notches 135 provided in the fixed portions 114 of the shelves, while the rear or after missile handling lugs or the-upper side of the missile are engaged by the transverse groove 110 in the rammer yoke.

In FIG. 4 is shown a fragmentary sectional view of the manner in which the hoist chain is fastened to the hoist. Referring to FIGS. 4 and 5, it Will be observed that the hoist chain is yrestrained and guided by a generally T- shaped channel or guide 94 which `consists of a body portion 136 holding the link structure and a pair of wing' channels or portions 137 forming tracks in which the chain rollers may roll. Carried at the end of the chain is a head 139 which is. attached to a T-shaped member Actuation then, of chain drive sprocket 96 will cause the.

chain to move in'its channel 94 and, because of the described connection, the hoist 85 will be lowered and raisedv During operation of the system, it will be understood that to obtain a stowed missile from the magazine for launching, the hoist .35 is horizontally aligned with the selected shelf as shown in FIG. 3. Rammer yoke cylinder 1% is actuated and the ramrner Vyoke 100 acting on the rear missile handling lugs 191 causes all three missiles (or as many as are on the shelf) to be slid in unison longitudinally in the magazine. This action disengages the lower missile handling lugs from the notches 135 in the fixed portions 114 of the shelves and causesthem to come to rest in the notches or grooves 134 in the transfer bars 116. Since the hoist is properly aligned, as illustrated in FlG. 3, T-catch 119 is engaged in buckle 117 and actuationof motor 128 causes the transfer chain 12) to draw the transfer bars 116 into the transfer bar channels 11S provided in the hoist surface. At this time, the auxiliary jack 139 is actuated contemporaneously with the rammer yoke 1li() to move themissiles in unison longitudinally back in the direction whence they came. The missiles remaining on the shelf are moved by the rammer yoke to occupy Ythe outermost positions or stations on the shelf with their missile handling lugs engaged by the notches 135 in the fixed shelf portions. The other missile is moved by auxiliary jack 130 so that its lugs are engaged by the notches 192 in the hoist. Motor 12Smay then be again actuated to return theV transfer bars 116 to their original position and the hoist is free to be elevated or lowered, as required. Y

In order to load a missile onto the storage shelves,l

the previously described procedure is substantially reversed. The missile on the hoist S5 is lowered to a position so that the Vhoist is horizontally aligned with the selected missile storage shelf. Assuming that the shelf already has two mizssileson it, they will be occupying the two outermost `stations'io-'r positions and the outer station must be cleared for receipt of the new missile. The rammer yoke 190 is actuated to cause the missile lugs to be moved into the notches 134 in the transfer bars 116. The transfer chain motor 128 is actuated to cause the transfer bars 116 to move the two missiles to the inner stations and the yoke 16) repositions them in notches 135. The transfer chain motor 128 is again actuated to cause the transfer bars 116 to be drawn into transfer bar channels 118 in ,the hoist. YIn this instance, only auxiliary jack 131 is actuated to force the missile to be loaded from its position on the hoist onto the transfer bars. The transfer bars are then, Aby means of the extendible .transfer chain 120, pushed back to theirLoriginal position in the shelf. The rammer yoke is again actuated'to seat the missile lugs firmly in the notches 135 provided in the fixed shelf portions. Had the shelf been empty prior to the loading operation it would obviously have been unnecessary to actuate the rammer yoke prior to drawingV the transfer bars into the hoist, since the outer station on the shelf would havealready been empty and ready for the receptionof the new missile. ,s

FIGS. 7 and 8 are respectively, plane and front elevational views with parts in section, showing .the rammer rail and the remmer chain and head. The rail 31 consists of a body-portion 144- whrich is provided in its outer ex-Y tremities with Van oppositely disposed pair of grooves V146V in which the forward handlingy lugs 101 ofthe missile may ride, and a T-shaped channel 148 alongrits bottom .longitudinal axis for carrying the after missile handling lugs. The outermost extremities of the T-shaped channel 148gare'grooved as Vat 15) to provide guide tracks for the spring loaded guide pin 151 of the rammer head V21;

Interiorly of the body portion 144 of the rail there is provided arecess 152v in which the chain links 32 may 9. ride, While lateral channels 153 of the recessV serve as tracks for the chain rollers 33.

The rammer head 21 is notched at 154 (FIG. l0) to engage the after missile lug 101 and is pivotally connected atv 156 to the rammer chain. The head 21, due to its pivotal connection 156, is free to move up and down with respect to the chain as its guide pin 151 follows the guide tracks 150. As mentioned heretofore, the guide pin 151 is preferably spring loaded or otherwise suitably biased to force the pins outwardly into following engagement with guide tracks 150. The Spanner rail and launcher rail are similarly configured to allow the rammer head 21, ramming a missile, to be slid horizontally along the rammer rail, across the extension provided by the spanner rail, onto the launcher rail.

As explained hereinbefore, the missiles may be carried aloft by hoist 85 with their lower or bottom missile handling lugs engaged in the notches or grooves 162 provided in the hoist surface.

Referring now to FIG. 9, the hoist is raised to a position where its upper missile handling lugs 101 enter cavities 158 and 159 formed in the rammer rail 31. At this time the rammer head 21 may be located at a position behind the missile and may be maintained here while the n and tail surfaces are affixed to the missile. When the missile is ready to be launched, auxiliary jack 130 is actuated which, by acting on after handling lug 101, causes the missile Vto be moved longitudinally out of engagement with the notch surfaces ltz'to the open keyways 103 in the hoist surface. As this sliding action is freeing the bottom missile handling lugs from engagement with the hoist notch surfaces, the upper handling lugs are seating in the lug grooves 146, 148 provided in the rammer rail.

FIG. l shows the position of the missile handling lugs 101 following the completed stroke of auxiliary jack 13). The upper lugs are engaged in the grooves 145, 148 of the rammer rail 31 while the lower or bottom lugs are in the keyways 103 of the hoist so that the missile is supported by the rammer rail.

The hoist 85 may then be lowered through the door assembly 68 and the door may be closed.

It is to be understood'that the tail and iin surfaces may be affixed after transfer of the missile to the rammer rail is'eifected and such action may be found desirable in order that the hoist may be more expeditiously retrieved within the magazine area.

As will be observed from FIGS. 9 and 10, the rammer head is provided with a cammed leading edge 16tl'so that as the rammer chain is moved toward the missile the' head may cam itself over the top surface of the after missile handling lug 101. To allow the head to slide over the after lug, the guide pin 151 should be free of its track. The arrangement illustrated provides that the guide pin groove 150 commence substantially with the grooves 146, 14S for the lugs. Behind the cavity 15S the rammer head 21 is free for limited up and down movement and is restrained from pivoting too far downwardly by abutment of surface 162 of the rammer head against the surface of the chain.

As the movement of the rammer chain forces the cammed head 21 over the after handling lug, the influence of gravity causes the head notch 154 to engage the lug in pushing relation. Further movement of the chain causes the spring loaded guide pin 151 to nd its track 15d and the missile is slid on its uper handling lugs toward the launcher rail 14.

When the missile is rammed onto the launcher rail to the desired launching position, the after missile lug should be released so that the rammer chain can be retracted and the blast doors 54 closed.

FIG. ll illustrates means for accomplishing the timely release of the rear missile lug. A release groove 164 is located in the launcher rail in communication with the normal groove track for the rammer head guide pin 151. The release groove 164 is a deeper groove than the norlil mal guide groove so that the spring loaded guide pin 151 will slip into the release groove 164. Since the release groove describes a path vertically above the normal track for the guide pin, the rammer head Z1 will raise following its guide pin to thereby release the missile. The missile is thus freed from the ramming action at the desired point on the launcher rail 14 and the ramming mechanism can be retracted for another cycle. On reversing the direction of rotation of the rammer drive sprocket, the rammer head 21 will be retracted. The guide pin will remain in the groove 164 till it merges with the normal guide track or groove 15) at point 165. It will be understood that merging portion 163 of groove 164 is shallower than track 150 to assure proper travel of the guide pin.

The release and engagement of the after handling lug 191 is further facilitated by the shape of the rammer head 21. By locating the pivotal connection of the rammer head 21 sufciently behind and slightly above the lugengaging notch 154 the radius of curvature described by the pushing surface 155 of the notch is kept within permissible limits to effect smooth operation of the release procedure. The position of the rammer head 21 in both extremes of its vertical movement is shown in FIG. l1.

When a missile is properly positioned on the launcher rail 14, and the rammer head retracted, the Spanner rail may be unlatched and housed and the blast doors 54 closed. The blast doors serve to isolate the interior of the system from blast effect when the booster is detonated to launch the missile. The back-scratcher 2t) may be lowered into contact with the missile to connect the interior missile components with an external source of power to warm the electronic components, furnish firing orders and the like.

When the missile is ready for launching, the backscratcher may be disconnected and raised to its normal position on the launcher arm as shown in FlG. l and the launcher trained and elevated in accordance with launching or gun orders. When the missile is launched, the blast effect is expended against the blast doors and housings without disturbing the interior of the system. Blast deflector 55 tends to deilect the gaseous blast from interfering with the train and elevation of the after launcher located above and behind the forward launcher.

Briefly summarizing, the launching system of the present invention is suitable for any permanent launching installation but is particularly well adapted for shipboard service. Each system may be utilized singly or may be used with other like systems, one desirable arrangement being the tandem installation disclosed.

The total complement of missiles for each launching system is stowed, completely assembled except for wingsV and fins, in a horizontal attitude below the main deck of the ship. In the magazine, missiles are stowed in tiers on each side of a center support. The depth and width of the `'space 76 may vary from ship to ship, thus causing a compensating change in the number of missiles per tier and/ or the number of tiers which can be stored.

Hoist lifts carry the missiles from the shelves to the fin and tail attachment stations where the assembly of the missiles is completed. Doors or hatches separate the magazines from the strike-down areas and fin assembly areas and the doors should be closed except when hoisting missiles therethrough.

The iin assembly station 22 is located behind its associated launcher and is on the same horizontal level. A ramming mechanism is suspended from the overhead of the assembly station and is used to ram the missiles horizontally to the launcher. A pair of blast doors separate the launcher and the fin and tail assembly station. A spanner rail is mounted inside the assembly station behind the blast doors and is adapted to be raised and held in a horizontal position to provide a continuous ramming track for ramming the missiles to the launcher rail.

It is desirable to keep the interior hatches closed when the blast doors are open to provide protection to the 1i li remainder of the system. Suitable interlocks could be provided if ldesired to ensure that, whenthe blast doors were open, the interior hatches would remain closed.

The system is intended to provide a means of firing missiles either singly or in salvo from the dual launcher. A tandem installation is obviously capable of firing a four missile salvo. The system of the present invention is intended to be completely automatic except for the manual attachmentv of iin and tail surfaces immediately prior to launching. l

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

l. A guided missile launching and handling system, said system positively securing the missiles against damaging movement thereof comprising a magazine for storing the missiles in a horizontal attitude in vertical tiers, said magazine including a plurality of cantilevered shelves and a hoist vertically movable in said magazine for raising and lowering the missiles, said shelves having a iiXed portion including a iirst releasable locking means for securing the missiles against movement and armovable transfer portion adjacent said xed portion for moving a selected one of the missiles to said hoist, said transfer portion including a second releasable locking meansfor securing the missiles` against` relative movement with respect to said transfer portion, means for shifting the missiles between said iirst releasable locking means on said iixed portion and said second releasable locking means on said transfer portion, a third releasable locking means included in said hoist for securing the selected missile against relative, movement therewith, means for shifting said selected missile between said second releasable loci;- ing means on said transfer portion and said third releasf able locking means on said hoist when said transfer portion has moved the selected missile from said shelves to lsaid hoist, a launching device, ramming means' aligned with said launching device and vertically aligned with said hoist for moving the selected missile from said hoist to said launching device and means for unlocking said third releasable locking means to allow said rammer to move the selected missile from said hoist to said launch# ing device. Y Y

2. The system as recited in claim 1 characterized by 'the missiles being of the type handled by external lugs mounted thereon and wherein said iirst, second and third releasable locking means incorporatesets of notches for matingly engaging the missile handling lugs.

gitudinally aligned magazines for storing the missiles in a horizontal attitude in vertical tiers, each magazine including a plurality of cantilevered shelves and a hoist for raising and lowering the missiles, said shelves having a Xed portion including a rst releasable locking means for securing the missiles against movement and a movable transfer portion adjacent the iXed portion for moving a selected one of the missilesfto said hoist, said transfer portion including a second releasable 'locking means for securing the missile against relative movement with respect to said transfer portion, means for shitting the mis Siles between said first releasrable locking means on said fixed portion and said second releasable locking means on said transfer portion, a third Vreleasable locking means included in said hoist for securing the selected missile i against relative movement, means for shifting said'selected missile between said second releasable locking means on said transfer portion and said third releasable locking Y means onsaid hoist when said transfer portion has moved the selected missile to said hoist, a plurality or" launching devices, each of said magazines being aligned with a launching device, a plurality of rammers, Veach rammer being aligned with one of said magazines and its associated launching device for moving the selected missile from said hoist to said launching device, means fory unlocking said third releasable locking means to allow said rammer to Y move the selected missile from said hoist to said launchingidevice and means, including said hoist, in each nfagazinef for transferring'missiles longitudinally among said plurality of magazines.

, References Cited by the Examiner UNITED STATES PATENTS BENJAMrN A.v BORCHELT, Primary Examiner. sAMUELfw; ENGLE, Examinar. 

1. A GUIDED MISSILE LAUNCHING AND HANDLING SYSTEM, SAID SYSTEM POSITIVELY SECURING THE MISSILES AGAINST DAMAGING MOVEMENT THEREOF COMPRISING A MAGAZINE FOR STORING THE MISSILES IN A HORIZONTAL ATTITUDE IN VERTICAL TIERS, SAID MAGAZINE INCLUDING A PLURALITY OF CANTILEVERED SHELVES AND A HOIST VERTICALLY MOVABLE IN SAID MAGAZINE FOR RAISING AND LOWERING THE MISSILES, SAID SHELVES HAVING A FIXED PORTION INCLUDING A FIRST RELEASABLE LOCKING MEANS FOR SECURING THE MISSILES AGAINST MOVEMENT AND A MOVABLE TRANSFER PORTION ADJACENT SAID FIXED PORTION FOR MOVING A SELECTED ONE OF THE MISSILES TO SAID HOIST, SAID TRANSFER PORTION INCLUDING A SECOND RELEASABLE LOCKING MEANS FOR SECURING THE MISSILES AGAINST RELATIVE MOVEMENT WITH RESPECT TO SAID TRANSFER PORTION, MEANS FOR SHIFTING THE MISSILES BETWEEN SAID FIRST RELEASABLE LOCKING MEANS ON SAID FIXED PORTION AND SAID SECOND RELEASABLE LOCKING MEANS ON SAID TRANSFER PORTION, A THIRD RELEASABLE LOCKING MEANS INCLUDED IN SAID HOIST FOR SECURING THE SELECTED MISSILE AGAINST RELATIVE MOVEMENT THEREWITH, MEANS FOR SHIFTING SAID SELECTED MISSILE BETWEEN SAID SECOND RELEASABLE LOCKING MEANS ON SAID TRANSFER PORTION AND SAID THIRD RELEASABLE LOCKING MEANS ON SAID HOIST WHEN SAID TRANSFER PORTION HAS MOVED THE SELECTED MISSILE FROM SAID SHELVES TO SAID HOIST, A LAUNCHING DEVICE, RAMMING MEANS ALIGNED WITH SAID LAUNCHING DEVICE AND VERTICALLY ALIGNED WITH SAID HOIST FOR MOVING THE SELECTED MISSILE FROM SAID HOIST TO SAID LAUNCHING DEVICE AND MEANS FOR UNLOCKING SAID THIRD RELEASABLE LOCKING MEANS TO ALLOW SAID RAMMER TO MOVE THE SELECTED MISSILE FROM SAID HOIST TO SAID LAUNCHING DEVICE. 